Arianegroup Gmbh

Astrium Gmbh

Eads Space Transportation Gmbh

Chris Udo Maeding

Axel Preuss

Jan Alting

A combustion chamber section for a combustion chamber for a rocket engine, the combustion chamber section including a combustion chamber body enclosing a combustion chamber volume and having coolant channels disposed therein, and at least one baffle integrally formed with the combustion chamber body and projecting from the combustion chamber body into the interior of the combustion chamber. The at least one baffle includes at least one coolant channel fluidly connected to at least one of the coolant channels in the combustion chamber body. Furthermore, an additive layer manufacturing method for manufacturing such a combustion chamber section is described.

Combustion chamber section with integral baffle and method of making a combustion chamber section

A combustion chamber for a rocket engine, the combustion chamber including a combustion chamber body enclosing a combustion chamber volume and a nozzle portion tapering in a longitudinal direction of the combustion chamber and adjoining the combustion chamber body. The combustion chamber body has at least one first portion and a second portion, wherein an inner surface of the at least one first portion facing the combustion chamber volume is closer to a cross-sectional center of the combustion chamber body than an inner surface of the second portion of the combustion chamber body. Furthermore, a additive layer manufacturing method for manufacturing such a combustion chamber is described.

Combustion chamber with vibration damping inner wall shape and method for manufacturing a combustion chamber

An injection apparatus for a rocket engine comprises an injection plate which delimits a combustion chamber upstream. The injection apparatus further comprises a plurality of coaxial injection elements distributed in the injection plate, each of which injection elements forms an inner outlet opening, delimited by a central sleeve body, for a first propellant component and an outer outlet opening for a second propellant component. The outer outlet opening is formed between the central sleeve body and a wall section which surrounds the central sleeve body in an annular manner. At least in a partial number of the injection elements, the central sleeve body projects from the wall section in the direction towards the combustion chamber. In particular, the central sleeve body projects relative to the injection plate into the combustion chamber.

Injection apparatus for a rocket engine

Embodiments of the invention relates to an injection element having an inner element with a first outlet opening and an outer element. The outer element includes at least one second outlet opening structured and arranged for receiving and injecting fuel in a combustion space, and arranged coaxially to the first outlet opening. The outer element further includes third outlet openings composed of bores structured and arranged for forming a cooling liquid film layer, wherein the bores are arranged coaxially to the first outlet opening and the at least one second outlet opening.

Injection element

The invention relates to an injection element having an inner element with a first outlet opening and an outer element. The outer element includes at least one second outlet opening structured and arranged for receiving and injecting fuel in a combustion space, and arranged coaxially to the first outlet opening. The outer element further includes third outlet openings composed of bores structured and arranged for forming a cooling liquid film layer, wherein the bores are arranged coaxially to the first outlet opening and the at least one second outlet opening.

A liquid fuel rocket engine with a closed direct auxiliary flow cycle has a combustion chamber connected to each liquid fuel source through a respective main liquid fuel supply line. A turbo pump is provided in each main fuel supply line. The turbo pump is driven by a gas generator which is connected to a first bypass fuel supply line for supplying fuel to the gas generator. An exhaust gas duct ( ) leads from the gas generator into at least one main fuel supply line for feeding gas generator exhaust gas into the main fuel supply line upstream of the turbo pump.

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Unterschleissheim, Germany

Chris Udo Maeding